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I.S.A. 571 (isa571-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: I.S.A. 571 (isa571-il)
Reynolds number: 100,000
Max Cl/Cd: 54.34 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-isa571-il-100000-n5.txt
Download as CSV file: xf-isa571-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: I.S.A. 571                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3973   0.10616   0.10128  -0.0236   1.0000   0.0383
  -8.750  -0.3989   0.10339   0.09859  -0.0241   1.0000   0.0384
  -8.500  -0.4013   0.10063   0.09590  -0.0243   1.0000   0.0384
  -8.250  -0.4004   0.09742   0.09275  -0.0254   1.0000   0.0384
  -8.000  -0.3979   0.09402   0.08940  -0.0268   1.0000   0.0384
  -7.500  -0.3916   0.08519   0.08059  -0.0243   1.0000   0.0291
  -7.250  -0.3883   0.08200   0.07744  -0.0240   1.0000   0.0280
  -7.000  -0.3843   0.07851   0.07398  -0.0256   1.0000   0.0276
  -6.750  -0.3782   0.07479   0.07028  -0.0277   1.0000   0.0276
  -6.500  -0.3696   0.07085   0.06633  -0.0303   1.0000   0.0279
  -6.250  -0.3584   0.06673   0.06217  -0.0329   1.0000   0.0280
  -6.000  -0.3447   0.06248   0.05786  -0.0355   1.0000   0.0279
  -5.750  -0.3289   0.05815   0.05344  -0.0379   1.0000   0.0275
  -5.500  -0.3101   0.05363   0.04878  -0.0405   1.0000   0.0271
  -5.250  -0.2884   0.04896   0.04392  -0.0431   1.0000   0.0269
  -5.000  -0.2641   0.04420   0.03889  -0.0455   1.0000   0.0270
  -4.750  -0.2360   0.03905   0.03333  -0.0479   1.0000   0.0283
  -4.500  -0.2038   0.03307   0.02669  -0.0504   1.0000   0.0304
  -4.250  -0.1804   0.03132   0.02476  -0.0506   1.0000   0.0320
  -4.000  -0.1513   0.02825   0.02119  -0.0515   1.0000   0.0344
  -3.750  -0.1198   0.02527   0.01750  -0.0524   1.0000   0.0400
  -3.500  -0.0849   0.02364   0.01554  -0.0541   0.9977   0.0448
  -3.250  -0.0370   0.02195   0.01340  -0.0583   0.9907   0.0545
  -3.000   0.0106   0.02060   0.01165  -0.0622   0.9822   0.0643
  -2.750   0.0537   0.01955   0.01041  -0.0652   0.9739   0.0694
  -2.500   0.0944   0.01884   0.00954  -0.0678   0.9666   0.0763
  -2.250   0.1292   0.01812   0.00875  -0.0691   0.9578   0.0793
  -2.000   0.1657   0.01744   0.00800  -0.0707   0.9496   0.0830
  -1.750   0.2028   0.01682   0.00736  -0.0724   0.9407   0.0872
  -1.500   0.2361   0.01634   0.00686  -0.0733   0.9293   0.0932
  -1.250   0.2701   0.01589   0.00642  -0.0744   0.9172   0.1044
  -1.000   0.3036   0.01540   0.00591  -0.0753   0.9038   0.1192
  -0.750   0.3364   0.01491   0.00548  -0.0760   0.8881   0.1439
  -0.500   0.3709   0.01427   0.00515  -0.0773   0.8705   0.2343
   0.250   0.4719   0.01204   0.00434  -0.0789   0.7938   1.0000
   0.500   0.5077   0.01202   0.00407  -0.0799   0.7562   1.0000
   0.750   0.5402   0.01213   0.00389  -0.0803   0.7149   1.0000
   1.000   0.5696   0.01234   0.00384  -0.0802   0.6739   1.0000
   1.250   0.5971   0.01263   0.00386  -0.0798   0.6358   1.0000
   1.500   0.6232   0.01295   0.00395  -0.0793   0.5987   1.0000
   1.750   0.6487   0.01330   0.00408  -0.0787   0.5629   1.0000
   2.000   0.6739   0.01363   0.00423  -0.0781   0.5307   1.0000
   2.250   0.6990   0.01398   0.00439  -0.0775   0.5021   1.0000
   2.500   0.7241   0.01433   0.00459  -0.0770   0.4772   1.0000
   2.750   0.7493   0.01470   0.00484  -0.0765   0.4575   1.0000
   3.000   0.7748   0.01505   0.00511  -0.0760   0.4408   1.0000
   3.250   0.8002   0.01541   0.00541  -0.0756   0.4257   1.0000
   3.500   0.8255   0.01579   0.00575  -0.0752   0.4107   1.0000
   3.750   0.8506   0.01616   0.00610  -0.0748   0.3962   1.0000
   4.000   0.8757   0.01654   0.00646  -0.0743   0.3825   1.0000
   4.250   0.9007   0.01693   0.00687  -0.0739   0.3700   1.0000
   4.500   0.9260   0.01729   0.00730  -0.0735   0.3586   1.0000
   4.750   0.9512   0.01768   0.00775  -0.0731   0.3479   1.0000
   5.000   0.9761   0.01808   0.00822  -0.0726   0.3367   1.0000
   5.250   1.0004   0.01849   0.00872  -0.0721   0.3236   1.0000
   5.500   1.0244   0.01889   0.00920  -0.0715   0.3093   1.0000
   5.750   1.0483   0.01932   0.00972  -0.0709   0.2958   1.0000
   6.000   1.0721   0.01974   0.01026  -0.0703   0.2815   1.0000
   6.250   1.0957   0.02017   0.01084  -0.0697   0.2667   1.0000
   6.500   1.1184   0.02058   0.01141  -0.0689   0.2444   1.0000
   6.750   1.1385   0.02111   0.01183  -0.0679   0.2073   1.0000
   7.000   1.1585   0.02185   0.01249  -0.0669   0.1810   1.0000
   7.250   1.1774   0.02279   0.01335  -0.0658   0.1518   1.0000
   7.500   1.1959   0.02385   0.01429  -0.0647   0.1008   1.0000
   7.750   1.2064   0.02593   0.01588  -0.0627   0.0405   1.0000
   8.000   1.2178   0.02783   0.01770  -0.0605   0.0292   1.0000
   8.250   1.2282   0.02970   0.01975  -0.0583   0.0246   1.0000
   8.500   1.2413   0.03112   0.02145  -0.0563   0.0226   1.0000
   8.750   1.2515   0.03270   0.02330  -0.0539   0.0214   1.0000
   9.000   1.2590   0.03440   0.02525  -0.0514   0.0203   1.0000
   9.250   1.2636   0.03619   0.02727  -0.0486   0.0192   1.0000
   9.500   1.2639   0.03804   0.02930  -0.0454   0.0181   1.0000
   9.750   1.2622   0.04013   0.03156  -0.0423   0.0172   1.0000
  10.000   1.2583   0.04252   0.03412  -0.0394   0.0164   1.0000
  10.250   1.2535   0.04518   0.03695  -0.0370   0.0159   1.0000
  10.500   1.2492   0.04806   0.03998  -0.0349   0.0155   1.0000
  10.750   1.2458   0.05118   0.04324  -0.0332   0.0152   1.0000
  11.000   1.2438   0.05449   0.04672  -0.0318   0.0149   1.0000
  11.250   1.2421   0.05805   0.05043  -0.0306   0.0147   1.0000
  11.500   1.2403   0.06143   0.05404  -0.0301   0.0146   1.0000
  11.750   1.2364   0.06517   0.05801  -0.0300   0.0145   1.0000
  12.000   1.2307   0.06929   0.06236  -0.0304   0.0144   1.0000
  12.250   1.2231   0.07381   0.06712  -0.0315   0.0143   1.0000
  12.500   1.2138   0.07877   0.07231  -0.0331   0.0142   1.0000
  12.750   1.2031   0.08417   0.07794  -0.0353   0.0141   1.0000
  13.000   1.1909   0.09004   0.08403  -0.0381   0.0141   1.0000
  13.250   1.1778   0.09634   0.09053  -0.0413   0.0141   1.0000
  13.500   1.1638   0.10307   0.09745  -0.0449   0.0141   1.0000
  13.750   1.1493   0.11021   0.10478  -0.0489   0.0141   1.0000
  14.000   1.1344   0.11777   0.11251  -0.0533   0.0142   1.0000
  14.250   1.1194   0.12570   0.12059  -0.0580   0.0143   1.0000
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